Airplane propeller



Apnl 17, 1945. J. B. GRADY 2,373,825

AIRPLANE PROPELLER Filed Feb. '7, 1944 5 Sheets-Sheet l Inventor April1945- J. B. GRADY AIRPLANE PROPELLER Filed Feb. 7, 1944 5 Sheets-Sheet 2J25 5/5 5 gmqm April 1945. J. B. GRADY AIRPLANE PROPELLER 5 Sheets-Sheet5 Filed Feb. 7, 1944 April 17, 1945.

J. B. GRADY AIRPLANE PROPELLER 5 Sheets-Sheet 4 J J L a I 20' t IInventor Ar JESS/E 5 Gamay By 2mm April 17, 1945. GRADY 2,373,825

AIRPLANE PROPELLER Filed Feb. 7, 1944 5 Sheets-Sheet 5 2 I I a J0Inventor 29 2; JZ$s/ 5. $240y Patented Apr. 17, 1945 "UNITED STATE sPATENT, "orncs 3 Claims.

The present invention relates to new and useful improvements inpropellers of the variable pitch type particularly for airplanes, andhas for its primary object to provide a device of this'charactercomprising a novel construction and arrangement for feathering theblades.

Other objects of the invention are to provide a variable pitch propellerof the character described which will be comparatively simple inconstruction, strong, durable, highly efllcient and reliable in use,compact, light in weight and which may be manufactured at low cost.

All of the foregoing, and still further objects and advantages of theinvention, will become apparent from a study of the followingspecification, taken in connection with the accompanying drawingswherein like characters of reference designate corresponding partsthroughout the several views, and wherein: v

Figure Us a view in side elevation of a variable pitch propellerconstructed in accordance with the present invention.

Figure 2 is a view in front elevation thereof.

Figure 3 is a view in vertical longitudinal section, taken substantiallyon the line 3-3 of Figure 2.

Figure 4 is a top plan view with a portion broken away in horizontalsection substantially on the line 4-4 of Figure 3.

Figure 5 is a cross sectional view, taken sub-.

stantially on the line 5-5 of Figure 1.

Figure 6 is a view in longitudinal section, taken substantially on theline $6 of Figure 5.

Figure 'l is a cross sectional view, taken substantially on the line 1-1of Figure 6.

Figure 8 is a view in elevation of one of the link assemblies.

Referring now to the drawings in detail, it will be seen that theembodiment of the invention which has been illustrated comprises a.flange I which is rigidly secured in any suitable manner to the nose 2of a plane. Projecting forwardly from the flange i is a tubular spindle3 which is open at both ends. A housing 4 is mounted for rotation on thespindle '3. Roller bearings 5 are provided for the housing 4. Thehousing 4, which constitutes the hub of the propeller, comprisescomplementai front and back sections 8 and 1, respectively, which aredetachably bolted together at l.

Extending rotatably through the tubular spindle 2 is a propeller shaft 9from the power plant of the plane. The shaft 8 is provided, at itsforward end, with a nose or cap ll. The cap II is bolted at II to theforward end of the housing 4, thus-connecting said housing to the shaft9 for actuation thereby. Retaining nuts l2 are threaded on they forwardend portion of the tubular spindle 3 for the front bearing 5 and thehousing 4. A lock washer I3 is provided between ,the nuts [2.

The stems i4 of blades l5 are journaled in roller bearings i6 which areprovided therefor in the housing 4. Collars I! are splined on the innerend portions of the stems i4 and engaged beneath the inner bearings ii.Retaining, nuts it for the collars ii are threaded on the stems i4.Tapered pins I! are driven into the nuts l8 and the stems i4 forpreventing loosening of said nuts. Trunnions 20 project from the collarll.

Mounted for longitudinal sliding movement on the tubular spindle 3 is asleeve 2| comprising a flange 22 on its forward end. Journaled on rollerbearings 23 on the sleeve 2i is a ring 24. The

rear end portion of the sleeve 2| is threaded to 3. The pairs of links3i are secured together by bolts 32 with spacers 33 therebetween.

Operating bars 34 extend rearwardly from the sleeve 2 i. The bars 34 areslidable in longitudinal ways 35 which are provided therefor in thetubular spindle 3 and which pass through the flange I. The bars 34extend rearwardly to be operated in any suitable manner from the cockpitor control cabin of the plane by the pilot.

It is thought that the operation of the invention will be readilyapparent from a consideration of the foregoing. Briefly, the hubassembly is driven from the power plant of the plane through the shaft 4and the cap iii thereon bolted at H to the housing 4. To increase ordecrease the pitch of the blades ii, the sleeve 2! is shiftedlongitudinally on the tubular spindle 3 through the medium of the bars35. When this occurs, the links ll turnthe collars I! which are fixed onthe stems ll of the blades i5. Rotation of the ring 24 on the sleeve 2|and the collars 28 on the stub shafts 2! permits operation of the linksII in a manner to rotate the stems l4. The housing 4 is adapted toreceive a suitable lubricant ance with the present invention will bereadily understood, and although a preferred embodiment of the de .ce isas illustrated and described. it is to be understood that changes in thedetails of construction and in the combination and arrangement of partsmay be resorted to which will fall within the scope of the invention asclaimed.

What is claimed is:

1. A propeller comprising a tubular spindle, means on one end of thespindle for mounting same on a support, a housing journaled on thespindle, a drive shaft extending rotatably through the spindle andsecured at one end to the housing for rotating same, blades rotatablymounted in the housing, a sleeve slidable on the tubular spindle, meansfor actuating said sleeve, and

in the housing, a sleeve slidabie on the tubular spindle, means foractuating said sleeve, and means operatively connecting the blades tothe sleeve for rotation thereby, the last-named means including a ringrotatably mounted on the sleeve, collars rotatably mounted on said ring,and links having one end pivotally connected to the collars and theirother ends pivotally connected to the blades.

3. A propeller oi. the character described comprising a flange formounting on the nose of an airplane, a tubular spindle projecting fromsaid flange, spaced bearings on said spindle, a, housing journaled onsaid bearings, a drive shaft extending rotatably through the spindle, acap on one end of the drive shaft secured to the housing for connectingsaid housing to the drive shaft for actuation thereby, a plurality ofblades including stems Journaled in the housing, collars fixed on saidstem, a sleeve slidable on the tubular spindle, a ring rotatably mountedon said sleeve, stub shafts radiating from the ring, collars iournaledon said stub shafts, pairs of links having one end pivotally connectedto the firstnamed collars and their other ends pivotally connected tothe second-named collars, and means for shifting the sleevelongitudinally on the tubular spindle for rotating the first-namedcollars for feathering the blades.

JESSIE B. GRADY.

